GB2538982A - Self-contained, electric contra rotating propeller propulsion apparatus for aircraft - Google Patents
Self-contained, electric contra rotating propeller propulsion apparatus for aircraft Download PDFInfo
- Publication number
- GB2538982A GB2538982A GB1509480.8A GB201509480A GB2538982A GB 2538982 A GB2538982 A GB 2538982A GB 201509480 A GB201509480 A GB 201509480A GB 2538982 A GB2538982 A GB 2538982A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- propulsion apparatus
- propeller propulsion
- rotating propeller
- firewall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 239000002131 composite material Substances 0.000 claims abstract description 11
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 8
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 8
- 239000000446 fuel Substances 0.000 claims abstract description 5
- 230000001133 acceleration Effects 0.000 description 3
- 239000004215 Carbon black (E152) Substances 0.000 description 2
- 229930195733 hydrocarbon Natural products 0.000 description 2
- 150000002430 hydrocarbons Chemical class 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000013475 authorization Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000009970 fire resistant effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
- B64C11/48—Units of two or more coaxial propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
- B64D2041/005—Fuel cells
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
Abstract
An electrically-powered contra-rotating propeller propulsion apparatus 15 for an aircraft comprises a carbon composite housing structure 16 containing a battery. The apparatus may comprise duplicate controls for operating either of the propellers as a single independent system or operating the propellers together. The apparatus may comprise twin motors, wherein each motor is powered and controlled separately. Means for in-flight recharging, such as batteries fuel cells or a generator, may be mounted on an aircraft using the apparatus. The apparatus may be bolted to a firewall 10 of an aircraft and may replace a piston engine driving a single propeller.
Description
SELF-CONTAINED ELECTRIC CONTRA ROTATING PROPELLER
PROPULSION APPARATUS FOR AIRCRAFT
This invention relates to a self-contained electric contra-rotating propeller propulsion apparatus and battery means integrated into a carbon composite structure that can be mounted directly in place of an existing piston engine powered propeller propulsion apparatus in a light aircraft.
Installation of the said apparatus raises an aircraft from single engine status to twin engine status increasing safety and the operational capabilities of the aircraft.
Single engine General Aviation (GA) aircraft commonly have a piston engine that drives a single propeller mounted at the front of an aircraft fuselage. The engine is mounted in a metal frame that is bolted to a substantial fire resistant fuselage bulkhead called a firewall. The engine is enclosed by cowlings to reduce turbulence and drag during flight and channel cooling air. The whole assembly is commonly known as a nose cone assembly. Other structures such as a nose wheel undercarriage assembly may also be mounted directly to the firewall, to the engine mounting frame or both.
The firewall is an integral and permanent structural part of the aircraft fuselage.
The acceleration and torsional loads generated by a propulsion apparatus during flight are transmitted to the aircraft fuselage most commonly by bolts in through-holes located in the firewall which secure the engine mounting frame to the firewall. The loads generated by the undercarriage nose wheel when taxing or manoeuvring the aircraft on the ground are also passed into the firewall.
In most aircraft designs it is possible to remove the engine and mounting frame at the firewall by removing the mounting bolts leaving the firewall unencumbered. Fuel pipes, mechanical linkages, pneumatic pipes and electrical cables that pass through the firewall and operate the piston engine can also be removed.
As the said electric propulsion apparatus generates significantly lower stress levels than similar power hydrocarbon engines there is no need to increase or strengthen the firewall mounting arrangements.
This invention provides a self-contained, electrically powered, twin motor, contra-rotating, twin propeller propulsion apparatus integrated into a carbon composite battery structure that can be mounted substantially in place of an aircraft's existing piston engine propulsion system utilising the existing firewall mounting arrangements. The carbon composite battery housing structure also functions to pass the acceleration and torsional loads from the propulsion apparatus to the firewall. Rechargeable battery means are integrated into the carbon composite structure to give the aircraft sufficient energy to take off, climb to cruise altitude and cruise some distance and land.
Electrical and electronic data governing the control of the apparatus and reporting the status of the propulsion and energy storage means is passed to the pilot cockpit and instrument panels through a two way electrical penetrator plate mounted for the purpose on the firewall. Each motor is powered and controlled independently.
The installation of the said apparatus raises an aircraft from single engine status to twin engine status with significant benefits to the aircraft certification, classification and operational authorisation. Where the electric propulsion apparatus is fitted in place of a hydrocarbon fuelled engine of similar power, the torsional and acceleration stress, engine vibration, thermal output and exhaust gas levels are much reduced offering benefits to airframe design.
In a further configuration of the invention additional batteries, fuel cells or an engine driven generator are fitted into the aircraft in a convenient place such as the wings or aft of the firewall to provide electric power to recharge the battery means in the nose assembly in flight or to power the propulsion system motors directly via an electrical penetrator plate mounted for the purpose in the firewall.
The following is a description of some of the specific embodiments of the invention and illustrates the substitution of a piston engine propulsion system by the said apparatus at an aircraft firewall, reference being made to the accompanying drawings in which:-Figure 1 shows in perspective, a typical piston engine propeller propulsion apparatus mounted in a metal frame bolted to an aircraft firewall. The nose cowlings are removed for clarity. Typically a single propeller is mounted for rotation as illustrated.
Figure 2 shows in perspective, an electric contra rotating propeller propulsion apparatus mounted to a carbon composite battery housing structure which is bolted to an aircraft firewall. The nose cowlings are removed for clarity. Typically two contra rotation propellers are mounted for rotation as illustrated.
Figure 3 is a side view of an aircraft fitted with an electric contra rotating propeller propulsion apparatus mounted to a composite battery structure showing the position of the apparatus and firewall in an aircraft fuselage. New cowlings to suit the profile of the aircraft and electric contra rotating propeller propulsion apparatus and composite battery structure are shown together with a nose wheel undercarriage.
Referring to Figure 1 an existing piston engine propeller propulsion apparatus 14 is removed from the aircraft firewall 10 by removing the bolts 11 and 12 and the two bolts on the opposite side (not shown) securing the mounting frame 13 to the firewall. Ancillary services and control means such as cables, electrical wires, fuel pipes, pneumatic tubes and mechanical rods operating and controlling the apparatus would be removed prior to removing the bolts and are not shown.
Figure 2 shows the electric contra rotating propeller propulsion apparatus 15 mounted on the front of the carbon composite battery housing structure 16 which is bolted to the firewall 10 at 11 and 12 together with two bolts on the opposite side (not shown).
Figure 3 shows the position of the firewall 10 in an aircraft and the outline of the electric contra rotating propeller propulsion 15 and composite battery structure 16 bolted to it with a typical outline of new cowlings 17 fitted to the apparatus to preserve the aerodynamic profile of the aircraft.
Claims (6)
- CLAIMS1 An electric contra-rotating propeller propulsion apparatus and carbon composite battery structure configured for mounting to an aircraft firewall by existing bolt-holes.
- 2 An electric contra-rotating propeller propulsion apparatus as claimed in claim 1 that has duplicate controls that can operate either of the contra rotating pair as a single independent system or both together.
- 3 An electric contra-rotating propeller propulsion apparatus as claimed in claim 1 and 2 that is classed in aviation legislation generally as a twin engine system.
- 4 An electric contra-rotating propeller propulsion apparatus as claimed in claim 1-3 that can be recharged in flight from batteries, fuel cells, or a generator mounted elsewhere in the aircraft for the purpose.
- An electric contra-rotating propeller propulsion apparatus as claimed in claim 1-4 that can be configured and installed in existing or new designs of aircraft.
- 6 An electric contra-rotating propeller propulsion apparatus substantially as described herein with reference to Figures 2-3 of the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1509480.8A GB2538982A (en) | 2015-05-30 | 2015-05-30 | Self-contained, electric contra rotating propeller propulsion apparatus for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1509480.8A GB2538982A (en) | 2015-05-30 | 2015-05-30 | Self-contained, electric contra rotating propeller propulsion apparatus for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB201509480D0 GB201509480D0 (en) | 2015-07-15 |
| GB2538982A true GB2538982A (en) | 2016-12-07 |
Family
ID=53677599
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1509480.8A Withdrawn GB2538982A (en) | 2015-05-30 | 2015-05-30 | Self-contained, electric contra rotating propeller propulsion apparatus for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2538982A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019016509A1 (en) * | 2017-07-20 | 2019-01-24 | Bae Systems Plc | Aircraft control system |
| EP3814226A4 (en) * | 2018-06-27 | 2022-03-23 | H3 Dynamics Holdings Pte. Ltd. | Distributed electric energy pods network and associated electrically powered vehicle |
| WO2022157241A1 (en) * | 2021-01-22 | 2022-07-28 | Blue Spirit Aero Sas | Aircraft propulsion module and aircraft |
| WO2022177577A1 (en) * | 2021-02-22 | 2022-08-25 | ZeroAvia, Inc. | Modular electric powertrain conversion for aircraft |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4426049A (en) * | 1981-07-31 | 1984-01-17 | Stewart Donald M | Dual propeller and engine drive system for aircraft |
-
2015
- 2015-05-30 GB GB1509480.8A patent/GB2538982A/en not_active Withdrawn
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4426049A (en) * | 1981-07-31 | 1984-01-17 | Stewart Donald M | Dual propeller and engine drive system for aircraft |
Non-Patent Citations (2)
| Title |
|---|
| Electroflight, "Advanced Engineering Show 2013" [online]. Available from: http://www.electro-flight.co.uk/news/16-info-2.html [Accessed 16 November 2015] * |
| Electroflight, "The first high performance, battery powered, electric aircraft" [online] 2013. Available from: http://www.electro-flight.co.uk/aeroplane/electroflight.html [Accessed 16 November 2015] * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019016509A1 (en) * | 2017-07-20 | 2019-01-24 | Bae Systems Plc | Aircraft control system |
| EP3814226A4 (en) * | 2018-06-27 | 2022-03-23 | H3 Dynamics Holdings Pte. Ltd. | Distributed electric energy pods network and associated electrically powered vehicle |
| WO2022157241A1 (en) * | 2021-01-22 | 2022-07-28 | Blue Spirit Aero Sas | Aircraft propulsion module and aircraft |
| WO2022177577A1 (en) * | 2021-02-22 | 2022-08-25 | ZeroAvia, Inc. | Modular electric powertrain conversion for aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| GB201509480D0 (en) | 2015-07-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |